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A wing alone aircraft has aerodynamic centre pitching moment coefficient of -0.126. If lift coefficient at zero AOA is 0.38 then, find Cm0. Consider Xcg=0.3.

Correct Answer: -0.107
Given, wing alone arrangement, CMac = -0.126, CL0 = 0.38. Now, Cm0 is given by, Cm0 = CMac + CL0* = -0.126 + 0.38* = -1.07.

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